Device and method for real-time processing of remote sensing data by remote sensing equipment linked to the cabin

Abstract

A device and method for real-time processing of remote sensing data by remote sensing equipment linked in the cabin, the device comprising at least two remote sensing devices and a computer unit, the remote sensing device and the computer unit are both arranged on the aircraft through a shockproof unit to achieve longitudinal vibration reduction and lateral non-swaying; wherein the shockproof unit comprises: a ground rail assembly arranged on the aircraft; an anti-vibration seat arranged on the ground rail assembly; and a device connector for connecting the remote sensing device or the computer unit to the anti-vibration seat. The present invention realizes functions such as linkage of remote sensing equipment, remote sensing data transmission and real-time processing of remote sensing data through computer remote control, and can control multiple remote sensing devices at fixed seats in the aircraft, which is safe and saves time for backing up and processing data, can quickly complete remote sensing tasks, and improves aviation remote sensing efficiency.

Description

Technical Field

[0001] The invention belongs to the field of remote sensing, and in particular relates to a device and method for real-time processing of remote sensing data by remote sensing equipment linked to an aircraft cabin. Background Art

[0002] Traditional manned aerial remote sensing refers to installing a remote sensing device in the cabin of the aircraft. During the flight, the remote sensing technicians operate the device and use it to collect the corresponding remote sensing data. After returning, the data is copied out and handed over to the data processing personnel for processing. The space in the cabin of traditional remote sensing aircraft is relatively small, and generally only one remote sensing device can be installed, and multi-source remote sensing data cannot be obtained at the same time; in addition, the traditional aerial remote sensing aircraft is only responsible for collecting data, and then after the aircraft lands, the data is taken to the hotel, and the data is processed using remote sensing software, and finally the results are submitted. Since the data cannot be processed in real time on the aircraft, the time for going to and from the hotel and processing the data in the hotel is increased, resulting in low efficiency of aerial remote sensing; for multiple remote sensing devices, multiple people are required to operate on the aircraft to complete the task, which increases the danger of multiple people walking back and forth on the aircraft, which is not conducive to the safety of the operator; in addition, the data cannot be processed in real time, which increases the time for data copying and data processing. Summary of the invention

[0003] In view of this, one of the main objectives of the present invention is to propose a device and method for real-time processing of remote sensing data by remote sensing equipment linked to the cabin, in order to at least partially solve at least one of the above-mentioned technical problems.

[0004] In order to achieve the above-mentioned object, as one aspect of the present invention, a device for real-time processing of remote sensing data by remote sensing equipment in a cabin is provided, comprising at least two remote sensing equipment and a computer unit, wherein the remote sensing equipment and the computer unit are both arranged on the aircraft through a shockproof unit to achieve longitudinal vibration reduction and lateral non-shaking;

[0005] Wherein, the anti-vibration unit comprises:

[0006] A ground rail assembly, provided on the aircraft;

[0007] an anti-vibration mount, disposed on the ground rail assembly; and

[0008] Equipment connector, used to connect remote sensing equipment or computer unit to anti-vibration mount.

[0009] As another aspect of the present invention, a device method for real-time processing of remote sensing data by remote sensing equipment in a cabin is also provided, comprising:

[0010] The linkage of multiple remote sensing devices is realized by using the above-mentioned device installed on the aircraft;

[0011] Transmitting data acquired by remote sensing equipment to a computer unit during flight;

[0012] During the flight, data processing software is used to process remote sensing data in real time, thus completing the real-time processing of remote sensing data.

[0013] Based on the above technical solutions, it can be seen that the device and method for real-time processing of remote sensing data by remote sensing equipment in the cabin of the present invention has at least one of the following advantages over the prior art:

[0014] 1. Remotely control multiple remote sensing devices through computer terminals, without the need for multiple people to operate on the aircraft. Only one person can complete the task that previously required multiple people;

[0015] 2. The operator operates at a fixed seat, avoiding the danger of the operator walking back and forth on the aircraft to operate multiple devices in traditional situations, thus ensuring the operator's safety;

[0016] 3. The operator can complete data transmission and data processing during the flight, eliminating the need for data processors to copy and process data on the ground, thus saving time;

[0017] 4. The remote sensing equipment, computer terminal, display, inverter and seat rail are fixedly connected, replacing the conventional operation of drilling holes on the aircraft cabin floor and then connecting them, avoiding damage to the floor and unnecessary structures, and ensuring the stability of the device;

[0018] 5. The present invention realizes functions such as linkage remote sensing equipment, remote sensing data transmission and real-time processing of remote sensing data through computer remote control. Multiple remote sensing equipment can be controlled at a fixed seat on the aircraft, which is safe and saves time for backup and data processing, and can quickly complete remote sensing tasks and improve aviation remote sensing efficiency;

[0019] 6. The present invention can complete remote sensing monitoring tasks faster and more stably than traditional manned aerial remote sensing, and can obtain two results: 1) multi-source remote sensing data; 2) real-time processed remote sensing data results; therefore, work efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a flow chart of a method for real-time processing of remote sensing data by remote sensing equipment in a cabin according to the present invention;

[0021] Figure 2 is a data processing flow chart of the present invention;

[0022] Figure 3 It is a schematic diagram of the device connection of the present invention;

[0023] Figure 4 It is a schematic diagram of the installation structure of the computer terminal of the present invention;

[0024] Figure 5 It is an enlarged structural schematic diagram of the anti-vibration seat of the present invention;

[0025] Figure 6 It is a schematic diagram of the connection between the aluminum frame and the seat rail of the present invention;

[0026] Figure 7 It is an enlarged schematic diagram of the structure of the seat floor rail of the present invention;

[0027] Figure 8 It is an enlarged schematic diagram of the groove connector of the present invention after being installed on the seat rail;

[0028] Fig. 9 It is an enlarged schematic diagram of assembling the fixing plate of the present invention on the groove connecting piece;

[0029] Fig.10 for Figure 7 An enlarged schematic diagram of a cross-sectional view taken along the AA direction;

[0030] Fig.11 is an enlarged schematic diagram of the groove connector of the present invention;

[0031] Fig.12 It is a schematic diagram of the structure of a groove connector with multiple mounting holes of the present invention;

[0032] Fig.13 It is a schematic diagram of assembling a groove connector structure with multiple mounting holes and a seat floor rail according to the present invention.

[0033] In the figure, the meanings of the reference numerals are as follows:

[0034] 1. Computer terminal; 2. Anti-vibration seat; 3. Positioning plate; 4. Rectangular aluminum plate; 5. Seat rail; 6. Aluminum frame; 7. C-type connector; 8. Load-bearing rod; 9. Gasket; 10. Spring; 11. Bottom plate; 12. Leather pad; 13. Fixing hole for rail bolt; 14. Fixing hole for rectangular aluminum plate and aluminum frame; 15. Shell; 16. Arc groove; 17. Circular groove; 18. Rectangular groove; 19. Circular baffle; 20. Fixing plate; 21. Rectangular connecting block; 22. Hollow part; 23. Mounting hole; 24. Fixing hole. DETAILED DESCRIPTION

[0035] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with specific embodiments and with reference to the accompanying drawings.

[0036] The present invention discloses a device for real-time processing of remote sensing data by remote sensing equipment in a cabin, characterized in that it comprises at least two remote sensing equipment and a computer unit, wherein the remote sensing equipment and the computer unit are both arranged on the aircraft through a shockproof unit to achieve longitudinal vibration reduction and lateral non-shaking;

[0037] Wherein, the anti-vibration unit comprises:

[0038] A ground rail assembly, provided on the aircraft;

[0039] an anti-vibration mount, disposed on the ground rail assembly; and

[0040] Equipment connector, used to connect remote sensing equipment or computer unit to anti-vibration mount.

[0041] In some embodiments of the present invention, the device connector is a C-type connector;

[0042] In some embodiments of the present invention, the C-shaped connector includes an upper C-shaped body and a lower C-shaped body; the curvature radius of the upper C-shaped body is greater than the curvature radius of the lower C-shaped body.

[0043] In some embodiments of the present invention, the anti-vibration mount comprises:

[0044] Base plate;

[0045] A gasket, arranged on the bottom plate;

[0046] a housing disposed on the gasket;

[0047] a spring disposed on the washer and located inside the housing; and

[0048] A load-bearing rod, arranged on a spring;

[0049] In some embodiments of the present invention, the anti-vibration seat further comprises a leather pad having a buffering function, and the leather pad is arranged at the bottom of the base plate.

[0050] In some embodiments of the present invention, the anti-vibration unit further comprises a positioning plate and an aluminum plate for improving stability, wherein the positioning plate and the aluminum plate are arranged between the bottom of the anti-vibration seat and the ground rail connector;

[0051] In some embodiments of the present invention, the anti-vibration unit further comprises an aluminum frame, the aluminum frame is fixed on the ground rail assembly, the aluminum plate is arranged on the aluminum frame; a plurality of mounting holes are arranged on the aluminum frame;

[0052] In some embodiments of the present invention, a plurality of load-bearing beams are provided on the aluminum frame.

[0053] In some embodiments of the present invention, the ground rail assembly comprises:

[0054] A seat floor rail having a groove thereon;

[0055] A groove connector having a fixing hole and at least one mounting hole; and

[0056] A fixing plate is used to fix the groove connector to the seat rail through the fixing hole.

[0057] In some embodiments of the present invention, the groove is provided with a plurality of rectangular grooves and a plurality of circular grooves along the axial direction, and the rectangular grooves and the circular grooves are distributed at intervals and are interconnected;

[0058] In some embodiments of the present invention, the groove connector includes circular baffles at both ends and a rectangular connecting plate in the middle;

[0059] In some embodiments of the present invention, the radius of the circular baffle is smaller than the radius of the circular groove, the width of the rectangular connecting plate is smaller than the width of the rectangular groove, the length of the rectangular connecting plate is equal to the length of the rectangular groove, and the diameter of the circular baffle is greater than the width of the rectangular groove;

[0060] In some embodiments of the present invention, the radius of the fixing plate is smaller than the radius of the circular groove.

[0061] In some embodiments of the present invention, the cross section of the groove is convex;

[0062] In some embodiments of the present invention, the rectangular connecting plate is provided with an arc groove for accommodating the fixing plate; the depth of the arc groove is greater than or equal to the thickness of the fixing plate.

[0063] In some embodiments of the present invention, the computer unit includes a computer terminal, a display and an inverter; the computer terminal, the display and the inverter are all arranged on the aircraft through a shockproof unit.

[0064] The present invention also discloses a method for real-time processing of remote sensing data by remote sensing equipment in a cabin, comprising:

[0065] The linkage of multiple remote sensing devices is realized by using the above-mentioned device installed on the aircraft;

[0066] Transmitting data acquired by remote sensing equipment to a computer unit during flight;

[0067] During the flight, data processing software is used to process remote sensing data in real time, thus completing the real-time processing of remote sensing data.

[0068] In some embodiments of the present invention, the method of processing remote sensing data includes:

[0069] Identify remote sensing data files that require priority processing;

[0070] Create a header file corresponding to the remote sensing data file;

[0071] Check the header file corresponding to the remote sensing data file to ensure that the total field of view and number of bands of the remote sensing equipment meet the index requirements;

[0072] If there is a problem with the remote sensing data, replace the new remote sensing software for inspection. After the inspection is completed, the remote sensing data file is subjected to radiation correction.

[0073] Performing geometric correction processing on the remote sensing data file after the radiation correction processing to obtain a geometric correction file;

[0074] After adding geographic information to the geometric correction file and stitching it into a complete image, the remote sensing data processing is completed.

[0075] In some embodiments of the present invention, the method for processing remote sensing data specifically includes:

[0076] 1) Determine the remote sensing data files that need to be processed first;

[0077] 2) Create the header file corresponding to the remote sensing data file. The specific methods include:

[0078] a. Create a header file A.hdr with the same name as the remote sensing data file A.dat;

[0079] b. Right-click the remote sensing data file A.dat, click "Properties", and record the number of bytes corresponding to "Size" ;

[0080] c. Determine the number of columns in the above remote sensing data file and number of bands , then follow the formula:

[0081] ; (1)

[0082] Calculate the number of lines in the file;

[0083] d. Use the text editor A.hdr to make the remote sensing data file readable;

[0084] 3) Use remote sensing software to check the remote sensing data file to ensure that the total field of view and number of bands of the remote sensing equipment meet the index requirements; the calculation formula for the total field of view is as follows:

[0085] ; (2)

[0086] in, is the field of view; is the flight strip width; For Hanggao;

[0087] 4) If there is any problem with the remote sensing data, replace the new remote sensing software for inspection. After the inspection is completed, the remote sensing data file can be subjected to radiation correction processing: that is, each pixel of each band is inverted according to its corresponding inversion coefficient to obtain the target radiation brightness value in front of the lens. The calculation formula is as follows:

[0088] ; (3)

[0089] in, and For the Pixel No. The slope and intercept of the band pixels, and The remote sensing data are energy level and Energy level Pixel No. Band pixel value; is the incident spectral radiance value, in units of ;

[0090] According to the radiation brightness value and The relational expression can be derived as follows:

[0091] ; (4)

[0092] Formula (4) can be used to calculate the incident spectral radiation brightness value of each pixel, thereby completing the radiation correction of the remote sensing data;

[0093] 5) Geometric correction of remote sensing data files: that is, based on the position and attitude data and the corresponding collinear equations, the original remote sensing images are resampled to eliminate the geometric distortion caused by the movement of the flight platform and remote sensing equipment, terrain undulations, and atmospheric refraction, and the original remote sensing images are corrected to the required mapping coordinate system. The specific calculation method is as follows:

[0094] The exterior orientation elements are divided into two categories: line elements and angle elements, with a total of six parameters; the line element is , the corner elements are , any image point The corresponding ground coordinates are According to the collinear equation, we can get:

[0095] ; (5)

[0096] in, is the focal length of the remote sensing device, Is The rotation matrix is ​​formed, let , then formula (5) can be transformed into:

[0097] ; (6)

[0098] set up Represented as a graphics coordinate system, represents the geocentric coordinate system, represents the local section coordinate system, express Coordinate system, represents the sensor coordinate system, represents the image space coordinate system, Represents the rotation matrix from the image coordinate system to the geocentric coordinate system, Represents the rotation matrix from the geocentric coordinate system to the local tangent plane coordinate system, Represents the local section coordinate system to The rotation matrix of the coordinate system, express The rotation matrix from the coordinate system to the sensor coordinate system, Represents the rotation matrix from the sensor coordinate system to the image space coordinate system;

[0099] The output data of position and attitude data is the navigation solution, including The origin of the coordinate system is in the geocentric coordinate system ( Coordinates of the system as well as The origin of the coordinate system is relative to the geographic coordinate system ( The rotation angle of the system , that is, the roll angle of the aircraft ( )、Pitch angle( ) and yaw angle ( );

[0100] Then the line elements and angle elements are:

[0101] ; (7)

[0102] ; (8)

[0103] in, For remote sensing equipment projection center Coordinates in the coordinate system, for The origin of the coordinate system is Coordinates in the spatial rectangular coordinate system, is the coordinate of the origin of the object space coordinate system in the geocentric coordinate system, which can be converted into the coordinate of the geocentric coordinate system by taking the average value of all the longitude, latitude and altitude data provided by the position and attitude data;

[0104] 6) Perform image stitching on remote sensing data files. The specific method is as follows:

[0105] a. Use the functions ENVI_OPEN_FILE, ENVI_FILE_QUERY, and ENVI_GET_SLICE of the remote sensing software ENVI to obtain remote sensing image data and position and attitude data;

[0106] b. Step 5) has corrected the original remote sensing image to the mapping coordinate system. Each two-dimensional point on the original remote sensing image The gray value of the corresponding point after geometric correction The grayscale value of each original remote sensing image after correction is the GPS two-dimensional coordinate of the center point of the remote sensing device projection center. According to the imaging ground resolution of the remote sensing device, the image projection method is selected, and the function ENVI_MAP_INFO_CREATE in the remote sensing software ENVI is used to add geographic information to each remote sensing image.

[0107] Then use the MOSAIC_DOIT function to stitch all remote sensing images with geographic information into a complete image;

[0108] 7) Submit the processed remote sensing data results.

[0109] The technical solution of the present invention is further described below by means of specific embodiments in combination with the accompanying drawings. It should be noted that the following specific embodiments are only used as examples, and the protection scope of the present invention is not limited thereto.

[0110] See attached Figure 1-Figure 13 , a method for real-time processing of remote sensing data by remote sensing equipment in a cabin of the present invention, such as Figure 1 As shown, the following steps are included:

[0111] 1) Secure the computer terminal to the aircraft cabin floor before the flight;

[0112] 2) Two or more monitors are fixed to the aircraft cabin floor before the flight;

[0113] 3) Before the flight, connect the above monitor to the computer terminal to ensure that the computer terminal displays normally;

[0114] 4) Before the flight, connect the computer terminal to two or more remote sensing devices respectively;

[0115] 5) Before the flight, connect the display, computer terminal and remote sensing equipment to the aircraft power supply to ensure that they are powered normally;

[0116] 6) Use computer terminals to remotely control all remote sensing equipment during flight to achieve linkage of multiple remote sensing equipment;

[0117] 7) Transmitting data acquired by remote sensing equipment to a computer terminal during flight;

[0118] 8) Use data processing software to process remote sensing data in real time during flight;

[0119] 9) Submit the processed remote sensing data results after the flight.

[0120] Wherein, the remote sensing device in step 6) is equipped with a computer, a Windows operating system is installed on the computer, and the software for controlling the remote sensing device is installed in the Windows operating system. The remote desktop control method is:

[0121] 1) Open the "Control Panel" in the remote sensing equipment computer operating system;

[0122] 2) Click "User Accounts and Family Safety";

[0123] 3) Click "Change Windows Password";

[0124] 4) Click "Create a password for your account";

[0125] 5) Set a password and click "Create Password" to obtain the user name and password of the remote sensing device computer;

[0126] 6) Open "Computer" properties and select "Remote Settings";

[0127] 7) Check "Allow remote assistance to connect to this computer" and select "Allow computers running any version of Remote Desktop to connect"; now the remotely controlled remote sensing device computer has been set up and can wait for the computer terminal to remotely control it;

[0128] 8) Check the IP address of the remote sensing equipment computer;

[0129] 9) Open the remote desktop program on the computer terminal, fill in the IP address of the remote sensing device computer, and then click "Connect";

[0130] 10) After connecting, enter the user name and password to enter the remote sensing device computer;

[0131] 11) Open the remote sensing device control software in the remote sensing device computer to control the remote sensing device.

[0132] Wherein, the method of data transmission in step 7) is:

[0133] 1) Find the folder where the data acquired during the flight are stored on the remote sensing equipment computer;

[0134] 2) Right-click this folder and select "Properties";

[0135] 3) Click the "Sharing" tab and click the "Advanced Sharing" button;

[0136] 4) Check "Share this folder", click "Apply", "OK" and exit;

[0137] 5) Right-click the folder to be shared and select "Properties"; on the "Security" page, click "Edit";

[0138] 6) Click "Add", type Everyone and click "OK", check "Full Control", "Modify", "Read and Execute", "List Folder Contents", "Read", click "Apply", "OK";

[0139] 7) In the computer terminal, open "Control Panel", "Network and Internet", "View network computers and devices" in sequence, find and enter the above shared folder, and copy the data in the folder to the computer terminal solid state drive.

[0140] Among them, Figure 2 As shown, the method for processing remote sensing data in step 8) includes:

[0141] (1) Determine the remote sensing data files that need to be processed first;

[0142] (2) Create the header file corresponding to the remote sensing data file. The specific method is:

[0143] a. Create a file A.hdr with the same name as the remote sensing data file A.dat;

[0144] b. Right-click the remote sensing data file A.dat, click "Properties", and record the number of bytes corresponding to "Size" ;

[0145] c. Determine the number of columns in the above remote sensing data file and number of bands , then follow the formula:

[0146] (1)

[0147] Calculate the number of lines in the file;

[0148] d. Use the text editor A.hdr to enter the following parameters and save:

[0149] ENVI

[0150] description = {

[0151] File Imported into ENVI.}

[0152] samples = S

[0153] lines=L

[0154] bands = D

[0155] header offset = 0

[0156] file type = ENVI Standard

[0157] data type = 12

[0158] interleave = bil

[0159] sensor type = Unknown

[0160] byte order = 0

[0161] wavelength units = Unknown

[0162] (3) Use the remote sensing software ENVI to check the remote sensing data file to ensure that the total field of view and number of bands of the remote sensing equipment meet the index requirements; the calculation formula for the total field of view is as follows:

[0163] (2)

[0164] in, is the field of view; is the flight strip width; For Hanggao;

[0165] (4) If there are any problems with the remote sensing data, replace the new remote sensing software for inspection. After the inspection is completed, the remote sensing data file can be subjected to radiation correction processing: that is, each pixel in each band is inverted according to its corresponding inversion coefficient to obtain the target radiation brightness value in front of the lens. The calculation formula is as follows:

[0166] (3)

[0167] in, and For the Pixel No. The slope and intercept of the band pixels, and Remote sensing data energy level and Energy level Pixel No. Band pixel value; is the incident spectral radiance value, in units of

[0168] According to the radiation brightness value and The relational expression can be derived as follows:

[0169] (4)

[0170] Formula (4) can be used to calculate the incident spectral radiation brightness value of each pixel, thereby completing the radiation correction of the remote sensing data;

[0171] (5) Geometric correction of remote sensing data files: that is, based on the position and attitude data and the corresponding collinear equations, the original remote sensing images are resampled to eliminate the geometric distortion caused by the movement of the flight platform and remote sensing equipment, terrain undulations, and atmospheric refraction, and the original remote sensing images are corrected to the required mapping coordinate system. The specific calculation method is as follows:

[0172] The exterior orientation elements are divided into two categories: line elements and angle elements, with a total of six parameters. , the corner elements are , any image point The corresponding ground coordinates are According to the collinear equation, we can get:

[0173] (5)

[0174] in, is the focal length of the remote sensing device, Is The rotation matrix is ​​formed, let , then formula (5) can be transformed into:

[0175] (6)

[0176] set up Represented as a graphics coordinate system, represents the geocentric coordinate system, represents the local section coordinate system, express Coordinate system, represents the sensor coordinate system, represents the image space coordinate system, Represents the rotation matrix from the image coordinate system to the geocentric coordinate system, Represents the rotation matrix from the geocentric coordinate system to the local tangent plane coordinate system, Represents the local section coordinate system to The rotation matrix of the coordinate system, express The rotation matrix from the coordinate system to the sensor coordinate system, Represents the rotation matrix from the sensor coordinate system to the image space coordinate system;

[0177] The output data of position and attitude data is the navigation solution, including The origin of the coordinate system is in the geocentric coordinate system ( Coordinates of the system as well as The origin of the coordinate system is relative to the geographic coordinate system ( The rotation angle of the system , that is, the roll angle of the aircraft ( )、Pitch angle( ) and yaw angle ( );

[0178] Then the line elements and angle elements are:

[0179] (7)

[0180] (8)

[0181] in, For remote sensing equipment projection center Coordinates in the coordinate system, for The origin of the coordinate system is Coordinates in the spatial rectangular coordinate system, is the coordinate of the origin of the object space coordinate system in the geocentric coordinate system, which can be converted into the coordinate of the geocentric coordinate system by taking the average value of all the longitude, latitude and altitude data provided by the position and attitude data;

[0182] (6) Perform image stitching on remote sensing data files. The specific method is as follows:

[0183] a. Use the functions ENVI_OPEN_FILE, ENVI_FILE_QUERY, and ENVI_GET_SLICE of the remote sensing software ENVI to obtain remote sensing image data and position and attitude data;

[0184] b. Step 5) has corrected the original remote sensing image to the mapping coordinate system. Each two-dimensional point on the original remote sensing image The gray value of the corresponding point after geometric correction The grayscale value of each original remote sensing image after correction is the GPS two-dimensional coordinate of the center point of the remote sensing device projection center. According to the imaging ground resolution of the remote sensing device, the image projection method is selected, and the function ENVI_MAP_INFO_CREATE in the remote sensing software ENVI is used to add geographic information to each remote sensing image:

[0185] map_info=ENVI_MAP_INFO_CREATE( / geographic,mc=mc, ps=ps)

[0186] Then use the MOSAIC_DOIT function to stitch all remote sensing images with geographic information into a complete image:

[0187] ENVI_DOIT, 'MOSAIC_DOIT', fid=mosaic_fids, pos=corr_pos, dims=corr_dims, out_name=outname_mosaic, r_fid=out_mosaic_fid, xsize=xsize, ysize=ysize, x0=x0, y0=y0, georef=1, map_info=mosaic_map_info, out_dt=2, pixel_size=ps, see_through_val=see_through_val, use_see_through=use_see_through;

[0188] (7) Submit the processed remote sensing data results.

[0189] The present invention provides a device for real-time processing of remote sensing data by remote sensing equipment in a cabin, such as Figure 3-4 As shown, it includes: 2 or more remote sensing devices, a computer terminal 1, 2 or more monitors, an inverter, a gigabit network cable, and a video data cable arranged on the aircraft. The remote sensing device, the computer terminal 1, the monitor, and the inverter are all installed in the aircraft cabin. The four corners of the bottom of the remote sensing device, the computer terminal 1, the monitor, and the inverter are all provided with anti-vibration seats 2. The remote sensing device, the computer terminal 1, the monitor, and the inverter are connected to the top of the anti-vibration seat 2 through a C-type connector (i.e., a device connector) 7. The bottom of the anti-vibration seat 2 is fixed to a positioning plate 3 through screws. The positioning plate 3 is connected to a rectangular aluminum plate 4 to increase the pressure area and increase stability. Figure 6As shown, the rectangular aluminum plate 4 is fixed on the aluminum frame 6, the aluminum frame 6 is fixed on the ground rail connector, and the ground rail connector is fixed on the seat ground rail 5, so that the remote sensing equipment, computer terminal, display, inverter and aircraft are connected as a whole, which can achieve both longitudinal vibration reduction and lateral non-swaying; the display is electrically connected to the graphics card in the computer terminal through a video data cable; the computer terminal 1 is electrically connected to two or more remote sensing devices through a network switch and a gigabit network cable; the display is electrically connected to the inverter through a 220V power line, the computer terminal is electrically connected to the inverter through a 220V power line, and the inverter is installed on the computer terminal. As shown Figure 4 As shown, it is a schematic diagram of the installation of the computer terminal of the present invention; the remote sensing equipment, display and inverter of the present invention also adopt the same installation structure.

[0190] The aircraft's onboard power supply provides 28V DC power to power the remote sensing equipment. The inverter is connected to the aircraft's onboard power supply and outputs 220V AC power to power the computer terminal and monitor.

[0191] The computer terminal includes hardware such as CPU, motherboard, memory, graphics card, solid state drive, gigabit network card, network switch, mouse, keyboard, chassis, etc., and is installed with Windows operating system.

[0192] Among them, Figure 5 As shown, the anti-vibration seat 2 includes a load-bearing rod 8, a gasket 9, a spring 10, a shell 15, a leather pad 12, and a base plate 11. The lower end of the load-bearing rod 8 is connected to the gasket 9, the gasket 9 is in contact with the top of the spring 10, the spring 10 is located in the shell 15, the bottom of the spring 10 is connected to the base plate 11, the base plate 11 is connected to the bottom of the shell 15, the leather pad 12 is located at the bottom of the base plate 11, and screw holes are provided at the four corners of the base plate 11.

[0193] Among them, the C-shaped connecting member 7 includes an upper C-shaped body and a lower C-shaped body. The curvature radius of the upper C-shaped body is larger than that of the lower C-shaped body. Two connecting screw holes are provided at the bottom of the lower C-shaped body, which can be connected to the anti-vibration seat 2 by screws, and can also be connected to the remote sensing equipment, computer terminal, display or inverter by screws; two connecting screw holes are provided at the top of the lower C-shaped body and the bottom of the upper C-shaped body, the top of the lower C-shaped body can be connected to the bottom of the upper C-shaped body by screws, and the top of the lower C-shaped body and the bottom of the upper C-shaped body can be connected to the remote sensing equipment, computer terminal, display or inverter by screws; the top of the upper C-shaped body can also be connected to the remote sensing equipment, computer terminal, display or inverter by screws.

[0194] Among them, Figure 6-11As shown, the seat floor rail 5 is provided with a groove, and the groove is provided with a plurality of rectangular grooves 18 and a plurality of circular grooves 17 along the axial direction, the rectangular groove 18 is adjacent to the circular groove 17, the rectangular groove 18 is connected with the circular groove 17, and the cross section of the hollow part 22 of the groove is convex, the floor rail connector includes a groove connector, a fixing plate 20 and a screw, the groove connector is located inside the groove, the groove connector has circular baffles 19 at both ends, and a rectangular connecting plate 21 in the middle, threaded holes (i.e., mounting holes 23) are provided in the middle of the circular baffles 19 at both ends, and the middle rectangular connecting plate 21 is also provided with a threaded hole (fixing hole 24) for fixing, the radius of the circular baffle 19 is smaller than the radius of the circular groove 17, the width of the rectangular connecting plate 21 is smaller than the width of the rectangular groove 18, the length of the rectangular connecting plate 21 is equal to the length of the rectangular groove 18, and the circular baffle 19 is provided with a plurality of rectangular connecting plates 21. The diameter of the plate 19 is greater than the width of the rectangular groove 18, which is conducive to the groove connector being directly placed into the groove from the top of the groove; the groove connector can be inserted into the hollow part 22 of the groove and move axially along the seat rail 16. When the rectangular connecting plate 21 of the groove connector moves partially into the circular groove 17 of the groove, the groove connector will not be separated from the groove, because a fixing plate 20 is also provided above the threaded hole of the rectangular connecting plate 21 in the middle of the groove connector, and a circular arc groove 16 for placing the fixing plate 20 is provided on the rectangular connecting plate 21. The depth of the circular arc groove 16 is equal to the thickness of the fixing plate 20, so that the fixing plate 20 is in the circular groove 17 of the groove, and the top of the fixing plate 20 is not higher than the top of the groove after the fixing plate 20 is installed, so as to avoid the top of the fixing plate 20 being higher than the top of the groove, affecting the installation of other components or causing damage by the protrusion. The radius of the fixing plate 20 is equal to the circular radius of the groove connector, and the radius of the fixing plate 20 is smaller than the radius of the circular groove 17 of the groove. The installation method of the groove connector is as follows: align the two circular baffles 19 of the groove connector with the circular groove 17 respectively, the groove connector falls into the groove, and the groove connector is moved so that the arc groove 16 is aligned with the circular groove 17. Figure 8-9 As shown, the fixing plate 20 is placed in the arc groove 16 , and after the fixing plate 20 is connected by screws, the groove connector will not move axially along the seat rail 16 in the groove.

[0195] In order to increase the number of mounting holes 23 on the groove connector, the groove connector can also be designed as follows Figure 12-13 In the structure, the rectangular connecting plate 21 can be extended at both ends, thereby increasing the number of mounting holes 23 and reducing the number of groove connectors.

[0196] The seat rail 16 is provided with a fixed seat for real-time operation, and the four legs of the fixed seat are fixedly connected to the circular threaded holes (mounting holes) in the groove connector by screws. The aluminum frame 6 is fixedly connected to the circular threaded holes in the groove connector by screws, and the groove connector is fixedly connected inside the groove, so that the seat, remote sensing equipment, computer terminal, display, inverter and aircraft are connected as one, forming a stable real-time operation structure; a plurality of load-bearing beams are provided in the middle of the aluminum frame 6, and two parallel sides of the aluminum frame 6 are respectively connected to the grooves of the seat rail 16.

[0197] Computer terminal: Lenovo graphics workstation, model ThinkStationP900, but not limited to this product;

[0198] Remote sensing equipment: Push-broom hyperspectral imager of Shanghai Institute of Technical Physics, Chinese Academy of Sciences, model PHI, but not limited to this product;

[0199] Monitor: Lenovo 23-inch monitor, model ThinkVision X23, but not limited to this product;

[0200] Network switch: Huawei Gigabit network switch, model S1700-16G, but not limited to this product.

[0201] It should be noted that the implementation methods not shown or described in the drawings or the text of the specification are all forms known to ordinary technicians in the relevant technical field and are not described in detail. In addition, the above definitions of each element are not limited to the various specific structures, shapes or methods mentioned in the embodiments, and ordinary technicians in the field can simply change or replace them, for example:

[0202] (1) Directional terms mentioned in the embodiments, such as "upper", "lower", "front", "back", "left", "right", etc., are only used to refer to the directions of the drawings and are not intended to limit the scope of protection of the present disclosure;

[0203] (2) The above embodiments may be used in combination with each other or with other embodiments based on design and reliability considerations. That is, the technical features in different embodiments may be freely combined to form more embodiments.

[0204] The specific embodiments described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A method for real-time processing of remote sensing data by remote sensing equipment in a cabin, comprising: The linkage of multiple remote sensing devices is realized by using the device installed in the aircraft to process remote sensing data in real time through the linkage remote sensing device in the cabin; The device for real-time processing of remote sensing data by remote sensing equipment in the cabin comprises at least two remote sensing equipment and a computer unit, wherein the remote sensing equipment and the computer unit are both arranged on the aircraft through a shockproof unit to achieve longitudinal vibration reduction and lateral non-swaying; wherein the shockproof unit comprises: a ground rail assembly arranged on the aircraft; an anti-vibration seat arranged on the ground rail assembly; and an equipment connector for connecting the remote sensing equipment or the computer unit with the anti-vibration seat; Transmitting data acquired by remote sensing equipment to a computer unit during flight; During the flight, the remote sensing data is processed in real time using data processing software, that is, the real-time processing of remote sensing data is completed; The method for processing remote sensing data comprises: Identify remote sensing data files that require priority processing; Create a header file corresponding to the remote sensing data file; Check the header file corresponding to the remote sensing data file to ensure that the total field of view and number of bands of the remote sensing equipment meet the index requirements; If there is a problem with the remote sensing data, replace the new remote sensing software for inspection. After the inspection is completed, the remote sensing data file is subjected to radiation correction. Performing geometric correction processing on the remote sensing data file after the radiation correction processing to obtain a geometric correction file; After adding geographic information to the geometric correction file and stitching it into a complete image, the remote sensing data processing is completed; The method for processing remote sensing data specifically comprises: 1) Determine the remote sensing data files that need to be processed first; 2) Create the header file corresponding to the remote sensing data file. The specific methods include: a. Create a header file A.hdr with the same name as the remote sensing data file A.dat; b. Right-click the remote sensing data file A.dat, click "Properties", and record the number of bytes corresponding to "Size" ; c. Determine the number of columns in the above remote sensing data file and number of bands , then follow the formula: ；（1） Calculate the number of lines in the file; d. Use the text editor A.hdr to make the remote sensing data file readable; 3) Use remote sensing software to check the remote sensing data file to ensure that the total field of view and number of bands of the remote sensing equipment meet the index requirements; the calculation formula for the total field of view is as follows: ；（2） in, is the field of view; is the flight strip width; For Hanggao; 4) If there is any problem with the remote sensing data, replace the new remote sensing software for inspection. After the inspection is completed, the remote sensing data file can be subjected to radiation correction processing: that is, each pixel of each band is inverted according to its corresponding inversion coefficient to obtain the target radiation brightness value in front of the lens. The calculation formula is as follows: ；（3） in, and For the Pixel No. The slope and intercept of the band pixels, and Remote sensing data energy level and Energy level Pixel No. Band pixel value; is the incident spectral radiance value, in units of ; According to the radiation brightness value and The relational expression can be derived as follows: ；（4） Formula (4) can be used to calculate the incident spectral radiation brightness value of each pixel, thereby completing the radiation correction of the remote sensing data; 5) Geometric correction of remote sensing data files: that is, based on the position and attitude data and the corresponding collinear equations, the original remote sensing images are resampled to eliminate the geometric distortion caused by the movement of the flight platform and remote sensing equipment, terrain undulations, and atmospheric refraction, and the original remote sensing images are corrected to the required mapping coordinate system. The specific calculation method is as follows: The exterior orientation elements are divided into two categories: line elements and angle elements, with a total of six parameters; the line element is , the corner elements are , any image point The corresponding ground coordinates are According to the collinear equation, we can get: ；（5） in, is the focal length of the remote sensing device, Is The rotation matrix is ​​formed, let , then formula (5) can be transformed into: ；（6） set up Represented as a graphics coordinate system, represents the geocentric coordinate system, represents the local section coordinate system, express Coordinate system, represents the sensor coordinate system, represents the image space coordinate system, Represents the rotation matrix from the image coordinate system to the geocentric coordinate system, Represents the rotation matrix from the geocentric coordinate system to the local tangent plane coordinate system, Represents the local section coordinate system to The rotation matrix of the coordinate system, express The rotation matrix from the coordinate system to the sensor coordinate system, Represents the rotation matrix from the sensor coordinate system to the image space coordinate system; The output data of position and attitude data is the navigation solution, including Coordinates of the origin of the coordinate system in the geocentric coordinate system as well as The rotation angle of the coordinate system origin relative to the geographic coordinate system , namely the roll angle, pitch angle and yaw angle of the aircraft; Then the line elements and angle elements are: ；（7） ；（8） in, For remote sensing equipment projection center Coordinates in the coordinate system, for The origin of the coordinate system is Coordinates in the spatial rectangular coordinate system, is the coordinate of the origin of the object space coordinate system in the geocentric coordinate system, which can be converted into the coordinate of the geocentric coordinate system by taking the average value of all the longitude, latitude and altitude data provided by the position and attitude data; 6) Perform image stitching on remote sensing data files. The specific method is as follows: a. Use the functions ENVI_OPEN_FILE, ENVI_FILE_QUERY, and ENVI_GET_SLICE of the remote sensing software ENVI to obtain remote sensing image data and position and attitude data; b. Step 5) has corrected the original remote sensing image to the mapping coordinate system. Each two-dimensional point on the original remote sensing image The gray value of the corresponding point after geometric correction The grayscale value of each original remote sensing image after correction is the GPS two-dimensional coordinate of the center point of the remote sensing device projection center. According to the imaging ground resolution of the remote sensing device, the image projection method is selected, and the function ENVI_MAP_INFO_CREATE in the remote sensing software ENVI is used to add geographic information to each remote sensing image. Then use the MOSAIC_DOIT function to stitch all remote sensing images with geographic information into a complete image; 7) Submit the processed remote sensing data results.

2. The method according to claim 1, characterized in that The equipment connector is a C-type connector; Wherein, the C-shaped connecting piece comprises an upper C-shaped body and a lower C-shaped body; the curvature radius of the upper C-shaped body is greater than the curvature radius of the lower C-shaped body.

3. The method according to claim 1, characterized in that The anti-vibration mount includes: Base plate; A gasket, arranged on the bottom plate; a housing disposed on the gasket; a spring disposed on the washer and located inside the housing; and A load-bearing rod, arranged on a spring; Wherein, the anti-vibration seat also includes a leather pad that plays a buffering role, and the leather pad is arranged at the bottom of the base plate.

4. The method according to claim 1, characterized in that: The anti-vibration unit further comprises a positioning plate and an aluminum plate for improving stability, wherein the positioning plate and the aluminum plate are arranged between the bottom of the anti-vibration seat and the ground rail connector; The anti-vibration unit further comprises an aluminum frame, which is fixed on the floor rail assembly, and the aluminum plate is arranged on the aluminum frame; a plurality of mounting holes are arranged on the aluminum frame; Wherein, a plurality of load-bearing beams are arranged on the aluminum frame.

5. The method according to claim 1, characterized in that The ground rail assembly comprises: A seat floor rail having a groove thereon; A groove connector having a fixing hole and at least one mounting hole; and A fixing plate is used to fix the groove connector to the seat rail through the fixing hole.

6. The method according to claim 5, characterized in that The groove is provided with a plurality of rectangular grooves and a plurality of circular grooves along the axial direction, and the rectangular grooves and the circular grooves are distributed at intervals and are interconnected; The groove connector includes circular baffles at both ends and a rectangular connecting plate in the middle; The radius of the circular baffle is smaller than the radius of the circular groove, the width of the rectangular connecting plate is smaller than the width of the rectangular groove, the length of the rectangular connecting plate is equal to the length of the rectangular groove, and the diameter of the circular baffle is larger than the width of the rectangular groove; The radius of the fixing plate is smaller than the radius of the circular groove; The cross section of the groove is convex; The rectangular connecting plate is provided with an arc groove for accommodating the fixing plate; the depth of the arc groove is greater than or equal to the thickness of the fixing plate.

7. The method according to claim 1, characterized in that The computer unit comprises a computer terminal, a display and an inverter; the computer terminal, the display and the inverter are all arranged on the aircraft through a shockproof unit.

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